Mtu Motoren-und Turbinen-union Munchen Gmbh

Hubert Grieb

Werner Schlosser

Burkhard Simon

Helmut-Arnd Geidel

Martin Albers

Gerhard Pellischek

Hagen Hanser

Wilfried Klussmann

A cooling arrangement for the cooling air of hypersonic jet engines comprises a heat exchanger in which the temperature of the cooling air is reduced by means of the fuel to be burnt in the engine. In order to keep the operating temperatures of the heat exchanger within controllable limits, a partial flow of the cooling air is branched off downstream of the heat exchanger and is admixed to the cooling air upstream of the heat exchanger for reducing the temperature.

Cooling arrangement for jet engines

A thermally stressed rotary connection of two coaxially aligned shafts includes two metallic coupling sleeves which are connected with the shafts by way of elastic intermediate layers. The two metallic sleeves engage one another. A ceramic centering sleeve is provided radially around the outside of the coupling sleeves and is shrunk onto the two shafts. The arrangement has the advantage of an effective connectability of different shafts such as ceramic or metal, in which case the two shafts may be connected with one another during the mounting. This allows undivided housings to be used.

Thermally stressed, torsionally rigid connection

A propfan turbine engine for an aircraft has a shroud and on the leading edge of the shroud, has one or several, preferably two, separate sector-like annular profile parts which via actuating devices can be moved from the shroud such that slots can be formed between the profile parts and the shroud. This arrangement prevents dangerous air-flow separations on the outside of the upper shroud region and on the inside of the lower shroud region at large angles of attack of the aircraft engine for both high and low power operation.

Propfan turbine engine

A nozzle for a hypersonic engine includes an axially displaceable mushroom-shaped central body. Two mutually opposing expansion flaps are provided which, when the flying Mach number is low, can be swivelled with respect to one another and, when the flying Mach number is high, can be swivelled apart. As a result, an extensive change of the divergence of the nozzle can be achieved while maintaining a high mechanical stiffness and a low leakage level.

Propelling nozzle for a hypersonic engine

A fuel feed method and apparatus for a turboramjet engine having a combustion chamber operable as a turbine engine afterburner and as ramjet engine combustion chamber is disclosed which features the concurrent injection of kerosene and hydrogen. At low Mach numbers, kerosene is the predominant fuel injected, while at growing speeds, hydrogen is injected in increasing proportions. This provides for a short combustion chamber length while minimizing the on-board fuel load and benefits especially small-size hypersonic aircraft.

Fuel feed method and apparatus for a turboramjet engine

A propfan turbo-engine has two shrouded propfan rotors arranged upstream of a gas turbine which are driven by a contra-rotating working turbine. In addition to a favorable flow onto the blades, a low weight of the engine can be achieved.

Propfan turbo-engine

An energy supply system for mobile electric weapons, for the operation of a storage unit, has a turbine which can be acted upon for a short time by a combustion chamber with hot gas of a high pressure and temperature. In the idling operation, the turbine is maintained at an idling speed by exhaust gas from a vehicle driving system. As a result, a fast charging of the storage unit is achieved, and at the same time, the space requirement of the storage unit and of the energy generating device is reduced.

Weapon system

The air ducts of a heat exchanger are formed of a plurality of duct sections arranged axially one after the other and are clamped together in sealed relation by tension pipes arranged in spaced relation within the respective ducts sections. The tension pipes are perforated to permit air flow between the ducts and heat exchange tubes connected thereto.

Heat exchanger comprised of sections detachably and sealably clamped

Composite changeover-type reaction power plant for propelling aircraft and spacecraft operating in subsonsic, supersonic and hypersonic regions, embracing a turbofan bypass engine with front fan, and a ramjet engine with a cycle corresponding to that of the fan, where the fan has individually independently supported, operationally counterrotating statorless rotors and variable fan blades which are feathered and immobilized during ramjet operation for low drag during said ramjet operation.

Combined multi-speed jet engine for the drive of airplanes and space

A variable-geometry turbocompressor is provided which includes a tandem variable stator downstream of a rotor stage. The tandem stator includes an inlet stator cascade and an outlet stator cascade arranged adjacent one another and each including variable guide vanes. To accommodate precise control of the air flow over various compressor operating conditions, the inlet and outlet stator cascades are provided with adjusting mechanisms for varying the position of their vanes independently of one another.

Variable-geometry turbocompressor

A shaped tube with an elliptical cross-section with a multichamber design for tubular heat exchangers is provided with at least two cross ribs passing through an interior space of the tube at a distance from one another. A method for making this tube provides for bending an endless metal strip into two semifinished products with congruent profiles. Each profile has the shape of an isosceles triangle with rounded vertices and an elongated leg. The semifinished products are then placed against one another so that the free end of the elongated leg of one semifinished product abut the triangle base edge of the other semifinished product.

Shaped tube with elliptical cross-section for tubular heat exchangers

A heat exchanger with at least one main tube, closed off at one end, into which compressed air, which is to be heated, is admitted and, after being heated, is removed. The main tube has at least two channel guideways which are separated from one another in the longitudinal direction. U-shaped or curved compressed air lines project from the main tube and contact the hot gases. Each compressed air line is connected at one end to the channel guideway of the main tube into which compressed air is admitted, and at its other end with the channel guideway through which the heated compressed air is removed. The compressed air lines are formed primarily from hollow bodies, which extend in the direction of flow of the hot gas and which preferably are tapered at the inflow and outflow ends in order to aid the flow.

Growing community of inventors

Germering, Germany

Hubert Grieb